EP1633629A2 - Low-profile brake-in-spool aircraft arresting systems - Google Patents
Low-profile brake-in-spool aircraft arresting systemsInfo
- Publication number
- EP1633629A2 EP1633629A2 EP04801950A EP04801950A EP1633629A2 EP 1633629 A2 EP1633629 A2 EP 1633629A2 EP 04801950 A EP04801950 A EP 04801950A EP 04801950 A EP04801950 A EP 04801950A EP 1633629 A2 EP1633629 A2 EP 1633629A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- tape
- spool
- arresting
- rotatable portion
- rotatable
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000009434 installation Methods 0.000 claims abstract description 13
- 230000007246 mechanism Effects 0.000 claims abstract description 13
- 238000010276 construction Methods 0.000 claims description 12
- 230000008878 coupling Effects 0.000 claims description 11
- 238000010168 coupling process Methods 0.000 claims description 11
- 238000005859 coupling reaction Methods 0.000 claims description 11
- 239000000463 material Substances 0.000 claims description 7
- 239000000853 adhesive Substances 0.000 claims description 5
- 230000001070 adhesive effect Effects 0.000 claims description 5
- 238000000926 separation method Methods 0.000 claims description 4
- AZDRQVAHHNSJOQ-UHFFFAOYSA-N alumane Chemical group [AlH3] AZDRQVAHHNSJOQ-UHFFFAOYSA-N 0.000 claims 1
- 230000004913 activation Effects 0.000 abstract description 3
- 230000009977 dual effect Effects 0.000 abstract description 2
- 239000006096 absorbing agent Substances 0.000 description 7
- 230000000712 assembly Effects 0.000 description 7
- 238000000429 assembly Methods 0.000 description 7
- 229910000831 Steel Inorganic materials 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- NIXOWILDQLNWCW-UHFFFAOYSA-N acrylic acid group Chemical group C(C=C)(=O)O NIXOWILDQLNWCW-UHFFFAOYSA-N 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 238000004873 anchoring Methods 0.000 description 1
- 238000009412 basement excavation Methods 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000012939 laminating adhesive Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 229920000728 polyester Polymers 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
- B60T8/00—Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force
- B60T8/32—Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration
- B60T8/321—Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration deceleration
- B60T8/325—Systems specially adapted for aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/02—Ground or aircraft-carrier-deck installations for arresting aircraft, e.g. nets or cables
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D2121/00—Type of actuator operation force
- F16D2121/02—Fluid pressure
Definitions
- This invention relates to arresting systems usable to arrest travel of a vehicle and, more particularly, to such systems capable of arresting the travel of an aircraft, such as a tactical fighter aircraft, under emergency or other conditions.
- Aircraft arresting systems have been in use for many years.
- Prior such systems of the present general type typically include a barrier net or tail-hook cable stretched transverse to a runway at a point along or at an end of the runway.
- the net or cable is attached at each end to energy absorber units positioned on opposite sides of the runway.
- each energy absorber unit utilizes a flexible tape wound on a reel whose rotation is controllably braked by a braking mechanism employing friction.
- each energy absorber unit typically had a height of the order of five to six feet, so that the two units were required to be set back a considerable distance on respective sides of the runway (e.g., set back about 200 to 300 feet) or, if located closer to the edge of the runway, were required to be installed below surface grade in concrete vaults of significant depth to accommodate the height of the absorber units.
- arrestment occurs when an aircraft, which may be traveling at high speed, engages the barrier net or tail-hook cable positioned across a runway. As the aircraft tail hook engages the cable, for example, displacement of the cable in the direction of aircraft travel begins to pull the arrestment tape out of the absorber units on opposite sides of the runway.
- each tape As each tape is unwound from a tape spool, it produces rotation of the tape spool about an axis of rotation aligned horizontally. Tape spool rotation is braked by a frictional or other brake unit positioned adjacent to the tape spool.
- a small gasoline engine or other arrangement may be incorporated for use in rewinding the tape after its deployment for arrestment of an aircraft.
- the degree of braking may be controlled by application of hydraulic pressure for brake activation.
- the profile of brake application with passage of time as the aircraft first engages the system and is then brought to a stop may be computer controlled. Such control enables efficient, non-destructive arrestment of aircraft travel, without exhausting the length of arrestment tape available on the tape reel in each absorber unit.
- Objects of the present invention are to provide new and improved arresting systems which may have one or more of the following characteristics and capabilities: - low profile, with system height of the order of one foot; - compliance with airport obstruction regulations to permit above-ground installation at the edge of a runway; - brake-in-spool configuration with a brake assembly positioned within the hub of each tape spool; - arresting tape maintained pre-tensioned on the tape spool; - tape spools configured for one-time use and replacement after an aircraft arrestment; - no rewind engine or other mechanism for rewinding of arresting tape after deployment; - system configured to enhance tape spool removal and replacement; - system enclosure configured to withstand roll-over by aircraft wheels; and - system enclosure using aircraft landing mats for upper cover and lower structure.
- an arresting system for aircraft arrestment, includes a support assembly, brake assemblies, tape spools and a coupling device.
- a first brake assembly is supported by the support assembly and includes a stationary portion, a first rotatable portion configured to support a first tape spool rotatable about a nominally vertical axis, and a braking mechanism to brake rotation of the first rotatable portion.
- a second brake assembly is supported by the support assembly in horizontally spaced relation to the first brake assembly. The second brake assembly may be of the same configuration as the first brake assembly.
- First and second tape spools are removably supported by the rotatable portions of the respective first and second brake assemblies.
- Each tape spool includes a spool hub configured to encircle and rotate with the respective rotatable portion and an arresting tape wound on the spool hub.
- Each arresting tape may comprise a length of tape wound in successive layers on the spool hub under tension with at least a portion of a tape layer detachably adhered to an underlying tape layer to maintain the arresting tape in a pre-tensioned condition prior to tape deployment and permit separation of tape layer during deployment, the portion detachably adhered having a length equal to only a small percentage of the length of tape.
- a tape spool, usable in an arresting system having a brake assembly including a rotatable portion configured to support the tape spool includes the following.
- a spool hub is configured to encircle the rotatable portion of the brake assembly and to be removably supported by the rotatable portion for rotation therewith.
- a length of arresting tape is wound on the spool hub and may be maintained in a pre-tensioned condition.
- the spool hub may include internal keying features configured to cooperate with external keying features of a rotatable brake assembly portion to enable slidable installation of a tape spool in fixed rotational relation to the rotatable portion.
- Fig. 1 is a view of an arresting system installed at the edge of a runway and attached to a tail-hook cable crossing the runway.
- Fig.2 is a further view of the arresting system of Fig. 1.
- Fig. 3 shows the arresting system with top panels removed.
- Fig. 4 is a sectional view of a brake assembly shown in Fig. 3 positioned within the hub of a tape reel of the arresting system.
- Fig. 5 is an expanded view of components of the brake assembly of Fig. 4.
- Fig. 6 is a sectional view of a tape reel of the Fig. 3 arresting system.
- Fig. 7 shows the tail-hook cable/arresting tape coupling device as included in the arresting system of Fig. 3.
- Fig. 1 is an overview of an arresting system 10 in accordance with the invention, which is illustrated as being installed along the edge of a runway surface.
- Arresting tapes 66a and 66b extending from system 10 are attached, via coupling device 14, to a tail-hook cable 16 positioned transverse to the runway.
- cable 16 is supported above the runway surface by disks 18, of rubber or other suitable material, to facilitate engaging of the cable by the tail hook of an aircraft whose forward motion along the runway is to be arrested.
- the vertical height of the arresting system as shown in Fig. 1 may be one foot or less, so as to meet relevant airport regulations controlling the height of objects permitted to be positioned at the runway edge as shown.
- Fig. 1 may be one foot or less, so as to meet relevant airport regulations controlling the height of objects permitted to be positioned at the runway edge as shown.
- FIG. 1 represents a raised portion of earth or other suitable material positioned contiguous to arresting system 10 and including inclined ramp portions. With such configuration, the wheels of an aircraft which leave the runway surface can safely run along portion 20 and overrun arresting system 10, while avoiding damage to either the aircraft or the arresting system.
- removable cover panels of arresting system 10 may be provided in the form of aluminum aircraft landing pads, of a type available for use in providing temporary landing surfaces, or of other suitable construction. In applications in which in-ground installation is appropriate, the limited system height is compatible with shallow excavation. The cover panels may be positioned at ground level, with aircraft overrun permitted as necessary. For reference, the arresting system as in Fig.
- Fig. 1 may, for example, provide capabilities for arrestment of an aircraft traveling at a speed of 190 knots with a kinetic energy of 50 million foot-pounds or more.
- single-use arresting tapes are employed in the Fig. 1 system, which is arranged to facilitate removal and replacement of tape spools following an aircraft arrestment.
- Fig. 2 shows the arresting system 10 of Fig. 1 with top panels 22a and 22b in place. Approximate dimensions of this embodiment of system 10 may be 3.6 meters in length, 1.2 meters in width and 0.3 meters in height. In the figures, dimensions are not necessarily to scale, but may be distorted for purposes of clarity of illustration.
- Fig. 3 is a view of arresting system 10 of Figs.
- the system includes a support assembly, brake assemblies, tape spools and other components and subsystems to be described.
- the support assembly 12 includes base panels 22c and 22d, which may be aircraft landing pads or of other suitable construction.
- interconnecting structural elements in a crossed configuration are employed to provide structural X-frames 24a and 24b.
- These X-frames are combined with a plurality of columnar support members, as represented by support member 26, which provide support for the upper cover panels 22a and 22b and effectively transfer vertical forces directly to the underlying surface supporting the arresting system 10.
- Additional support for the cover panels is provided by constructing the structural members associated with operational portions of the arresting system (e.g., tape runout roller assembly 28 and hydraulic subsystem enclosure 30) to provide sufficient strength to support the cover panels and transfer forces to the underlying surface during an aircraft rollover and in other circumstances.
- Cover panels 22a and 22b may be fastened to upper portions of the support assembly (e.g., via bolts or other suitable arrangement) in a manner facilitating removal for replacement of tape spools or other service or maintenance activities.
- the Fig. 3 arresting system includes first and second brake assemblies 40a and 40b, which are mounted to the support assembly base panels 22c and 22d. At the top, each brake assembly is mechanically coupled to upper support member 32, which is removably attached to the enclosure 28.
- each brake assembly is positioned within the hub of one of the respective tape spools 60a and 60b to be further described.
- the height of a brake assembly is not additive to the height of the associated tape spool. Removal of upper support member 32 enables removal and replacement of tape spools 60a and 60b.
- Brake assembly 40a is shown in sectional view in Fig. 4. Brake assembly 40b as included in Fig. 3 is identical to assembly 40a. Basic components of this configuration of brake assembly 40a are further illustrated in the expanded view of Fig. 5.
- Vertically aligned support shaft 34 is part of the support assembly 12 and is mounted to the base of the support assembly.
- Brake assembly 40a includes a stationary portion 42, shown as an annular core member, supported by support shaft 34.
- Brake assembly 40a also includes a rotatable portion 44, shown as an annular external shell member, which is configured to support tape spool 60a, as will be further described. Coupled between stationary portion 42 and rotary portion 44, brake assembly 40a includes a braking mechanism 46, shown as comprising rotor disks 47, 48, 49, 50 and interspersed stator disks 51, 52, 53. In this configuration, the rotor disks 47- 50 are keyed at their outer circumference to the inner surface of rotatable portion 44, so as to rotate with rotation of portion 44.
- Interspersed stator disks 51-53 are keyed at their inner circumference to the outer surface of stationary portion 42, to prevent their rotation.
- Rotor disks 47-50 are provided with frictional surface linings and stator disks 51-53 are provided with steel wear surfaces.
- hydraulic system elements including components positioned under hydraulic subsystem enclosure 30 and which may include small pistons in the base of the brake assembly. Such a piston arrangement may be employed to enable application of hydraulic pressure to compress together the disks 47-53 between upper and lower pressure disks 55 and 60. Application of hydraulic pressure for this purpose may be suitably computer controlled in order to provide appropriate braking forces for effective aircraft arrestment.
- Brake assembly 40a may additionally include a cap portion 54, a cover 57, base ring 58, base flange 59, and other elements suitable for operationally positioning and maintaining brake assembly 40a and its components in position on support shaft 34.
- brake assemblies and constituent components may be employed as determined by skilled persons as appropriate to particular applications. It will thus be seen that, with internal elements of brake assembly 40a non- rotationally supported by the support assembly 12, via support shaft 34, and external elements including shell portion 44 rotatable, rotation of rotatable portion 44 can be controllably braked by frictional engagement of rotor disks 47-50 with stator disks 51-53.
- the braking mechanism 46 is positioned within a spool hub when the arresting system is assembled as in Fig. 3 and the tops of the brake mechanisms and tape spools are all at nominally the same height.
- Brake configurations utilizing friction between rotor and stator disk arrangements have previously been employed in aircraft arresting systems.
- the brake components have been positioned externally to a tape spool (e.g., side-by-side, with axes of rotation aligned horizontally) with mechanical coupling between a rotatable tape spool and rotatable elements of the brake which were internal to the brake.
- a prior configuration of this type (the BAK-12 Energy Absorber) has been marketed by the assignee of the present invention. While operationally effective, the BAK-12 unit does not provide a low-profile configuration usable in an above-ground installation along the edge of a runway.
- a first tape spool 60a of Fig. 3 is shown in more detail in Fig. 6.
- Second tape spool 60b as included in Fig. 3 is identical to tape spool 60a.
- first tape spool 60a includes a spool hub 62 to which are attached spool flanges 64a and
- Flanges 64a and 64b are identical, so that tape spool 62 may be installed with either flange as the top flange, depending upon whether tape deployment with clockwise or counter-clockwise spool rotation is desired, as will be further discussed.
- the spool components may be formed of steel or other suitable material and may be fastened together by screws or otherwise fabricated in one or more pieces.
- spool hub 62 includes internal keying features, shown as vertical grooves 62a, which are configured to cooperate with external keying features of rotatable portion 44 of the brake assembly 40a.
- the view of rotatable portion 44 included in Fig. 6 illustrates external ridges 44a dimensioned to mate with the grooves 62a.
- spool hub 62 can be slideably positioned around rotatable portion 44.
- the tape spool and rotatable portion are in fixed rotatable relation, so that any rotation of the tape spool during tape deployment for aircraft arrestment will produce accompanying rotation of the rotatable portion of the brake assembly.
- braking of rotatable portion 44 will produce braking of tape spool 60a.
- This construction enables tape spool 60a to be slideably installed on and removed from support by the brake assembly 40a for replacement of the tape spool after an aircraft arrestment.
- tape spool 60a also includes an arresting tape 66a wound on spool hub 62.
- Tape 66a may be of flat woven construction, of polyester or other suitable material, of the order of six inches wide, one-tenth inch thick and 800 feet in length or of other suitable dimensions and construction.
- the tape 66a is pre-tensioned when wound on spool hub 62, in order to avoid or mitigate slack conditions when an aircraft tail hook engages the tail-hook cable and thereby initiates arresting tape deployment.
- an adhesion element 68 may be positioned between at least a portion of a layer of the arresting tape and an underlying layer of the tape as wound on the tape spool.
- adhesion element 68 may be a patch of fabric or other material of suitable size, shape and thickness and bearing an adhesive substance on each main surface. With element 68 positioned as shown and covered by one or more layers of the wound tape, it is held in place and effective to maintain the pre-tensioned condition for the preceding windings of the tape. While the degree of pre-tensioning desirable may depend on tape stretch coefficients and other factors, a pre-tension of the order of one to two thousand pounds tangential pull may be effective for present purposes. The degree of adhesion and separability of the layers of the arresting tape and the characteristics and quantity and type of adhesive substance can be determined by skilled persons in view of operational parameters in particular implementations.
- an acrylic laminating adhesive such as Adhesive 468 manufactured by 3M Corporation
- Adhesive 468 manufactured by 3M Corporation
- the arresting system utilizes tape spools on a one-time basis, with removal and replacement of tape spools after each aircraft arrestment. Removal and replacement may also be desirable after an extended period of non-use of the system.
- the illustrated tape spool design is considered to provide a reliable tape spool of economical construction which enhances ease of installation and removal.
- skilled persons may provide different or variant tape spool configurations as appropriate for particular implementations of the invention.
- the arresting tape of tape spools 60a and 60b of Fig. 3 leaves the spools in a mirror-image relation, so that when an aircraft tail hook engages tail- hook cable 16, coupling device 14 pulls the arresting tapes from both tape spools 60a and 60b simultaneously. This causes tape spool 60a to rotate clockwise and tape spool 60b to rotate counter-clockwise.
- the tape spools are constructed to permit installation with either one of the spool flanges 64a or 64b of Fig. 6 as the top flange. At installation, the tape spools can thus be flipped over as appropriate to achieve the tape exit relationship as illustrated in Fig. 3, whereby the two arresting tapes can be fed out through the tape run-out rollers of assembly 28 in parallel side-by-side contiguous relationship.
- Fig. 7 illustrates an embodiment of coupling device 14, which is shown in Figs. 1 and 3 attached to one end of the arresting tape of each of first and second tape spools 60a and 60b, to enable attachment to an aircraft engagement unit, shown in Fig. 1 as tail-hook cable 14.
- Fig. 7 illustrates an embodiment of coupling device 14, which is shown in Figs. 1 and 3 attached to one end of the arresting tape of each of first and second tape spools 60a and 60b, to enable attachment to an aircraft engagement unit, shown in Fig. 1 as tail-hook cable 14.
- coupling device 14 includes top and bottom plates 70a and 70b configured to retain two arresting tape attachment pins 72a and 72b and tail-hook cable attachment pin 74. As shown, coupling device 14 includes additional spacer cylinders and threaded retainers. In other configurations, coupling device 14 may be of any suitable form, construction and material as appropriate to detachably connect the three elements and provide adequate strength in a particular application of the invention. In use, the ends of the arresting tapes of tape spools 60a and 60b are fastened around the respective tape attachment pins 72a and 72b and the end of the tail-hook cable is fastened around attachment pin 74.
- coupling device 14 is constructed to permit removal of threaded retainers positioned on the tops of the pins to permit removal of top plate 70a to enable pre-formed tape and cable end loops to be placed over respective attachment pins and secured in place by replacement and securing of top plate 70a.
- Other components and assemblies of the Fig. 3 arresting system include the tape run-out roller assembly 28 and a hydraulic subsystem indicated at 30.
- Assembly 28 may include tape-handling rollers arranged so that when tape deployment occurs the two tapes 66a and 66b are deployed in side-by-side parallel contiguous relationship as represented in Fig. 3.
- Subsystem 30 is arranged to enable controlled application of hydraulic pressure to the first and second brake assemblies 40a and 40b for braking of rotation of the first and second tape spools 60a and 60b in a coordinated manner, which may be computer controlled for effective aircraft arrestment.
- sensors may be employed to monitor rotation of the tape rollers in assembly 28, to provide data for use in deriving indications as to aircraft position and velocity usable for computer control.
- an arresting system utilizing the invention may be implemented by skilled persons in view of the preceding description and the description provided in the above noted US patent 5,042,750.
- the above description is provided in the context of an aircraft arresting system.
- the invention may also be employed in a wide variety of other applications in which it is desirable to arrest travel of a moving object, particularly when it is desirable to do so under controlled and non-destmctive conditions.
- the low over-all system height e.g., one foot or less
- the one- foot height may be earth-banked in above-ground installations or require only shallow provision for below-ground installations.
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Transportation (AREA)
- Regulating Braking Force (AREA)
- Tires In General (AREA)
- Braking Arrangements (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/440,744 US6779756B1 (en) | 2003-05-19 | 2003-05-19 | Low-profile brake-in-spool aircraft arresting systems |
PCT/US2004/015454 WO2005021378A2 (en) | 2003-05-19 | 2004-05-18 | Low-profile brake-in-spool aircraft arresting systems |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1633629A2 true EP1633629A2 (en) | 2006-03-15 |
EP1633629B1 EP1633629B1 (en) | 2012-10-24 |
Family
ID=32869287
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04801950A Expired - Lifetime EP1633629B1 (en) | 2003-05-19 | 2004-05-18 | Low-profile brake-in-spool aircraft arresting systems |
Country Status (4)
Country | Link |
---|---|
US (1) | US6779756B1 (en) |
EP (1) | EP1633629B1 (en) |
IL (1) | IL171616A (en) |
WO (1) | WO2005021378A2 (en) |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7467909B2 (en) * | 2006-03-30 | 2008-12-23 | Engineered Arresting Systems Corporation | Arresting systems and methods |
US8028952B2 (en) * | 2008-03-31 | 2011-10-04 | The Boeing Company | System for shipboard launch and recovery of unmanned aerial vehicle (UAV) aircraft and method therefor |
KR100929484B1 (en) | 2009-07-17 | 2009-12-02 | 한국항공우주산업 주식회사 | Braking device for unmanned aerial vehicle |
US8007198B1 (en) | 2010-03-02 | 2011-08-30 | Engineered Arresting Systems Corporation | Arresting systems and methods |
CN107310744B (en) * | 2017-06-09 | 2019-12-17 | 重庆零壹空间航天科技有限公司 | suspension and release mechanism for aircraft launching |
CN110844103B (en) * | 2019-12-23 | 2023-12-19 | 安徽天路航空科技股份有限公司 | Blocking device with buffering function |
CN111762332B (en) * | 2020-07-09 | 2022-06-07 | 四川航天烽火伺服控制技术有限公司 | Fixed wing unmanned aerial vehicle friction disc power consumption rope hook recovery unit |
CN113665832B (en) * | 2021-08-13 | 2024-03-15 | 航天时代飞鹏有限公司 | Unmanned aerial vehicle intelligent airport ground system |
CN115214744A (en) * | 2022-07-25 | 2022-10-21 | 泰安科创矿山设备有限公司 | Energy absorber and sports car protector |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3044614A (en) * | 1961-03-07 | 1962-07-17 | Hanscom & Co Inc H F | Tape package having controlled unwinding |
GB1081537A (en) * | 1964-06-30 | 1967-08-31 | Borje Fonden | Device for braking a landing aircraft |
US3236479A (en) * | 1965-02-26 | 1966-02-22 | Nordtorp Folke Karl Gustaf | Means for decelerating aeroplanes |
US3309043A (en) * | 1965-03-22 | 1967-03-14 | Bliss E W Co | Rapid cycle arresting system |
US3350039A (en) * | 1965-10-18 | 1967-10-31 | Wilbur D Crater | Clutching means for launching and arresting aircraft and the like |
US3434591A (en) * | 1967-01-26 | 1969-03-25 | Hanscom & Co Inc H F | Pancake type package having controlled unwinding |
US3497166A (en) * | 1967-07-14 | 1970-02-24 | Us Navy | Tape pendant connector |
US3581848A (en) | 1968-12-19 | 1971-06-01 | Gulf & Western Ind Prod Co | Aircraft arresting device with centrifugal brake |
US3578272A (en) * | 1969-07-08 | 1971-05-11 | Gulf & Western Ind Prod Co | Aircraft arresting device |
US3695559A (en) | 1970-05-20 | 1972-10-03 | Gulf & Western Ind Prod Co | Aircraft arresting apparatus |
FR2190641B1 (en) * | 1972-06-26 | 1976-01-16 | Aerazur Constr Aeronaut | |
US4102518A (en) | 1975-08-06 | 1978-07-25 | Aerazur Constructions Aeronautiques | Aircraft arresting gear |
US4101100A (en) * | 1976-07-28 | 1978-07-18 | Value Engineering Company | Aircraft flight line servicing system |
US4147317A (en) | 1977-06-23 | 1979-04-03 | All American Industries, Inc. | Mobile RPV landing deck |
US5042750A (en) | 1989-11-16 | 1991-08-27 | Datron, Inc. | Aircraft arresting system |
US6382869B1 (en) | 1999-12-09 | 2002-05-07 | Harry D. Dickinson | Above grade mass displacement trafficway barrier |
-
2003
- 2003-05-19 US US10/440,744 patent/US6779756B1/en not_active Expired - Lifetime
-
2004
- 2004-05-18 WO PCT/US2004/015454 patent/WO2005021378A2/en active Application Filing
- 2004-05-18 EP EP04801950A patent/EP1633629B1/en not_active Expired - Lifetime
-
2005
- 2005-10-27 IL IL171616A patent/IL171616A/en active IP Right Grant
Non-Patent Citations (1)
Title |
---|
See references of WO2005021378A2 * |
Also Published As
Publication number | Publication date |
---|---|
EP1633629B1 (en) | 2012-10-24 |
US6779756B1 (en) | 2004-08-24 |
WO2005021378A3 (en) | 2005-04-21 |
WO2005021378A2 (en) | 2005-03-10 |
IL171616A (en) | 2010-06-30 |
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